Progress in Thrust Measurements from Micro Pulsed Plasma Discharges

Emhoff, Jerold; Simon, Daniel; Land, Bruce R.

doi:10.2514/6.2007-5299

Cited by 9 publications

(3 citation statements)

References 4 publications

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“…The motion is measured through a Michelson interferometer and the impulse bit can then be derived by the dynamics of the flexure. The advantages of this type of thrust stand are small size, controllable sensitivity, and high resonance frequency (Emhoff, Simon, & Land, 2007).…”

Section: Design Of Test Bench For Measurement Of Thrust and Impulse Bmentioning

confidence: 99%

Design of Test Bench for Measurement of Thrust and Impulse Bits of MEMS-based Micro-thrusters

Sheikh¹,

Shabbir²,

Chatha³

et al. 2018

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Section: Design Of Test Bench For Measurement Of Thrust and Impulse Bmentioning

confidence: 99%

Design of Test Bench for Measurement of Thrust and Impulse Bits of MEMS-based Micro-thrusters

Sheikh¹,

Shabbir²,

Chatha³

et al. 2018

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“…The impulse exerted is determined by measuring velocities before and after the impact. 1,4,5 Another way to generate an impulse is to integrate the force recorded during the impact by a force transducer. 6,7 This impact calibration technique is effective in delivering momenta of the order of ∼1 mN s. When the impulse bit drops to ∼10 μN · s or less, accurate measurements become problematic.…”

Section: Introductionmentioning

confidence: 99%

Precision electromagnetic calibration technique for micro-Newton thrust stands

Zhang

et al. 2013

Review of Scientific Instruments

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This paper introduces a new direct non-contact electromagnetic calibration technique for high precision measurements of micro-thrust and impulse. A ring-shaped electromagnet with an air gap is used in the calibration. The calibration force is produced by the interaction of a uniform magnetic field with a copper wire current in the air gap. This force depends linearly on this current as well as the steady angular displacement of the torsion arm of the thrust stand. The range of calibration force is very large and the calibration force is easy to generate and insensitive to the arm displacement. The calibration uncertainty for a 150-μN force is 4.17 μN. The more influential factor on the calibration uncertainty is the magnetization of the electromagnet core due to the copper wire current. In the impulse calibration, the exerted impulse is linearly dependent on the maximal angular displacement of the torsion arm. The uncertainty in the impulse calibration is determined by uncertainties in both the force calibration and the pulse time.

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“…A thrust stand was developed to accurately measure thrust produced by microthrusters in University of Tokyo, and deflection of the torsional balance was detected by the linear variable differential transducer (LVDT) (Koizumi et al, 2004). Polzin et al (2006) designed an electric propulsion thrust stand capable of supporting testing of thrusters producing thrust levels between 100 μ N to 1 N. Emhoff et al (2007) designed a vibration type thrust measuring device with flexible metal structure, and the device was more sensitive to the vibration interference. Thrust measurement of a rectangular hypersonic nozzle was carried out by using an inclined baffle plate, which provided an on-axis force measurement and was applied to measure the magnitude and angle of the thrust vector (Araki et al, 2012).…”

Section: Introductionmentioning

confidence: 99%

The thrust measurement system research for combined nozzle in small space

Lü

Zhang

et al. 2018

Transactions of the Institute of Measurement and Control

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For measuring the thrust of combined nozzles in satellite thruster with a small space, the test method that the nozzle directly sprays on the load baffle is employed in this paper. The key problem is how to design the positions of 10 load baffles and how to construct the measurement system. A set of complete and automatic nozzle thrust measurement system is designed and built, and the influence of the load baffle applied on the flow field of nozzles is analyzed using the software FLUENT. Furthermore, the load surface locations of the sensors for the different types of nozzles are analyzed. We draw the conclusion that the load baffle position should range from 4–8 mm for the I-type nozzle and range in 6–12 mm for II-type and III-type nozzle. The correction coefficients of the thrust forces for all channels of the measurement system are determined in the calibration experiment. The uncertainty of measurement system is estimated and the error source of the measurement system is traced. We found that the systematic uncertainty is mainly contributed by the A-type uncertainty which is related with the nozzle dimension and its inner structure. The B-type uncertainty of system is contributed by the force sensor.

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Progress in Thrust Measurements from Micro Pulsed Plasma Discharges

Cited by 9 publications

References 4 publications

Design of Test Bench for Measurement of Thrust and Impulse Bits of MEMS-based Micro-thrusters

Design of Test Bench for Measurement of Thrust and Impulse Bits of MEMS-based Micro-thrusters

Precision electromagnetic calibration technique for micro-Newton thrust stands

The thrust measurement system research for combined nozzle in small space

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